Abstract: Process for guiding an elongated missile, equipped with booster motor, sustainer, power source, control electronics, payload, and search head, from above, upon a target, such as a helicopter, where the missile, after ballistic flight, is braked before the target area by a drogue chute and is diverted into a position that is essentially perpendicular to the earth's surface over the target area so that the search head of the missile, which is suspended from the drogue chute, will be pointed downward, whereupon, after the search head has locked on the target, the drogue chute is separated and the missile is guided to the target by the sustainer, characterized in that, immediately prior to, before, or after the moment of drogue chute deployment, a lateral motor, located in the center of gravity of the missile, is turned on so that, first of all, in order to accelerate the tilt-off of the missile into the vertical, there is generated a force that is added vectorially to the force of gravity and that thereupon one

Abstract: A method for determining the rates of turn of the missile/target line of sight with a seeker head rigidly mounted on the missile, characterized in that the azimuth and elevation deviation angles (.psi..sub.sm and .THETA..sub.sm) of the target measured with the rigidly mounted seeker head (2) in the missile-fixed coordinate system (s.sub.1, S.sub.2, s.sub.3) are transformed to the azimuth and elevation deviation angles (.psi..sub.v and .THETA..sub.v) of the target based on the coordinate system (v.sub.1, v.sub.2, v.sub.3) of a virtual, gimbal mounted and gyrostabilized seeker head (2v) that tracks the missile/target line of sight (SL) by rotation with the rates of turn (p.sub.v, q.sub.v, r.sub.v) about its three axes (v.sub.1, v.sub.2, v.sub.3).